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process simultaneously. To compare the thermal behavior for two configurations, a reference line (l1, illustrated in Fig. 1b) is selected on the plasma-on side of the airfoil to map the temperature distribution. III. Results Figure 3 shows the snapshots of the instantaneous images extracted from the high-speed camera results for two different configurations and J. AIRCRAFT, VOL. 57, NO. 2: ENGINEERING NOTES 385 Fig. 2 Schematic illustrations of original and optimized actuators. the plasma-off side at t 143 s when the heat of the plasma discharge reached a balanced state. Figure 4 exhibits the corresponding surface temperature distributions recorded simultaneously using the IR cam- era. Figure 5 illustrates the extracted profiles of surface temperature for sample lines l1. For the plasma-off side of the airfoil, as demonstrated in Fig. 3c, the evident ice accretion on the airfoil surface is observed, which would cause a lift reduction and drag increment due to the contami- nation of the streamlined profile over the airfoil. Figure 3a clearly illustrates the presence of the uniform ice at the leading edge and the fingerlike rivulet structures of ice accretion downstream of the actuator for the plasma-on side for the original design. Figure 4a shows the corresponding upper surface temperature distribution, which confirms the ice accretion in the same area. Figure 5 shows the corresponding surface temperature at l1. It shows that the temperature corresponding to the icing (i.e., the “frozen temperature”) in the present test is about −3°C due to the presence of incoming flow and the water film. The reason for the fingerlike rivulet structures of ice accretion is that, in the presence of incoming flow, the temperature of the plasma discharge is within 30°C [32]; the supercooled droplets cannot be vaporized at that low temperature. But, the supercooled water droplet would be efficiently heated and kept at the liquid state, and it would Fig. 3 Ice accretion snapshot over airfoil for different actuators and the plasma-off side for t 143 s, U∞ 40 m∕s, T∞ −10°C, and LWC 1.0 g∕m3. Fig. 4 Infrared images of ice accretion over airfoil for different actuator configurations and the plasma-off side for t 143 s, U∞ 40 m∕s, T∞ −10°C,andLWC1.0g∕m3. Downloaded by IOWA STATE UNIVERSITY on June 29, 2020 | http://arc.aiaa.org | DOI: 10.2514/1.C035697PDF Image | Optimization of Dielectric Barrier Discharge Plasma Actuators for Icing Control
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